Patent search ap:("Daniel David Snook" OR "Andrew Mitchell Rodwell") AND inv:"Daniel David Snook" Page 3

21.

发明申请
CLEARANCE CONTROL SYSTEM FOR A GAS TURBINE 有权
Title translation: 用于气体涡轮机的间隙控制系统

公开(公告)号：US20130266418A1

公开(公告)日：2013-10-10

申请号：US13442155

申请日：2012-04-09

Applicant: Daniel David Snook

Inventor： Daniel David Snook

IPC: F04D27/00

CPC classification number: F01D11/24 , F05D2260/201 , F05D2260/213

Abstract: A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.

Abstract translation: 公开了一种用于燃气轮机的间隙控制的系统，包括外涡轮机壳体，内涡轮机壳体和限定在内涡轮机壳体和外涡轮机壳体之间的气室。间隙控制系统可以包括设置在增压室内的冲击箱。冲击箱可以限定多个冲击孔。此外，间隙控制系统可以包括与冲击箱的内部流动连通的第一管道和在冲击箱外部的位置处与集气室流动连通的第二管道。

22.

发明申请
POWER PLANT AND METHOD OF OPERATION 有权
Title translation: 动力装置和操作方法

公开(公告)号：US20120023963A1

公开(公告)日：2012-02-02

申请号：US13217713

申请日：2011-08-25

Applicant: Lisa Anne Wichmann , Daniel David Snook , Noémie Dion Ouellet , Scott Allen Rittenhouse

Inventor： Lisa Anne Wichmann , Daniel David Snook , Noémie Dion Ouellet , Scott Allen Rittenhouse

IPC: F02C9/54 , F02C9/20 , F02C9/26 , F02C9/00

CPC classification number: F02C9/42 , F02C3/34 , F02C9/18

Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.

Abstract translation: 至少一个主要空气压缩机使压缩的环境气体流动。压缩的环境气体流以大于或基本上等于从每个涡轮压缩机作为再循环气流的至少第一部分输送到每个涡轮机燃烧器的输出压力的压力被输送到主涡轮燃烧器和从属涡轮机燃烧器。燃料流被输送到每个涡轮机燃烧器，并且形成并燃烧可燃混合物，形成再循环的气体流。制造主和从属涡轮机功率，并且每个主要和从属涡轮机功率基本上等于旋转每个涡轮压缩机所需的至少一个功率。再循环气体的至少一部分通过再循环回路再循环。再循环气体流的至少第二部分绕过燃烧器，或者每个再循环气体流的多余部分被排出或两者。

23.

发明申请
POWER PLANT AND METHOD OF OPERATION 有权
Title translation: 动力装置和操作方法

公开(公告)号：US20120023962A1

公开(公告)日：2012-02-02

申请号：US13217658

申请日：2011-08-25

Applicant: Lisa Anne Wichmann , Daniel David Snook , Samuel David Draper , Noémie Dion Ouellet , Scott Allen Rittenhouse

Inventor： Lisa Anne Wichmann , Daniel David Snook , Samuel David Draper , Noémie Dion Ouellet , Scott Allen Rittenhouse

IPC: F02C9/00

CPC classification number: F02C6/06 , F02C3/34 , F02C9/18 , F05D2260/85 , F05D2270/301

Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to a turbine combustor at a pressure that is greater than or substantially equal to an output pressure delivered to the turbine combustor from a turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to the turbine combustor, and a combustible mixture is formed and burned, forming the recirculated gas flow. A turbine power is produced that is substantially equal to at least a power required to rotate the turbine compressor. At least a portion of the recirculated gas flow is recirculated through a recirculation loop. An excess portion of the recirculated gas flow is vented or a portion of the recirculated gas flow bypasses the turbine combustor or both.

Abstract translation: 至少一个主要空气压缩机使压缩的环境气体流动。压缩的环境气体流以大于或基本上等于从涡轮压缩机作为再循环气流的至少第一部分输送到涡轮机燃烧器的输出压力的压力被输送到涡轮机燃烧器。燃料流被输送到涡轮机燃烧器，并且形成并燃烧可燃混合物，形成再循环气体流。产生的涡轮功率基本上等于至少旋转涡轮压缩机所需的功率。再循环气流的至少一部分通过循环回路再循环。再循环气流的一部分被排出，或者再循环气流的一部分绕过涡轮机燃烧室或两者。

24.

发明授权
Airfoil core shape for a turbine nozzle 有权
Title translation: 涡轮喷嘴的翼型形状

公开(公告)号：US08057169B2

公开(公告)日：2011-11-15

申请号：US12138580

申请日：2008-06-13

Applicant: Edward Durell Benjamin, Jr. , David John Humanchuk , Daniel David Snook

Inventor： Edward Durell Benjamin, Jr. , David John Humanchuk , Daniel David Snook

IPC: F03B3/12

CPC classification number: F01D5/141 , F05D2220/3212 , F05D2250/74 , F05D2260/202

Abstract: An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.

Abstract translation: 制品包括具有翼型芯形状的物体。翼型芯形状具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，每一个定义翼型轮廓部分距离Z以英寸为单位。在Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型芯形状。

25.

发明授权
Blade/disk dovetail backcut for blade/disk stress reduction (7FA+e, stage 1) 有权
Title translation: 用于刀片/盘片应力降低的刀片/盘燕尾背切（7FA + e，第1阶段）

公开(公告)号：US07476083B2

公开(公告)日：2009-01-13

申请号：US11476095

申请日：2006-06-28

Applicant: Daniel David Snook , John Herbert Dimmick, III , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin

Inventor： Daniel David Snook , John Herbert Dimmick, III , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin

IPC: F01D5/30

CPC classification number: F01D5/30 , F05D2230/10

Abstract: Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

Abstract translation: 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡燃气轮机叶片的机械性能。从材料去除区域去除材料会最大化平衡。

26.

发明申请
BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (7FA+E, STAGE 1) 有权
Title translation: 刀片/碟片减速刀片（7FA + E，第1级）

公开(公告)号：US20080260534A1

公开(公告)日：2008-10-23

申请号：US11476095

申请日：2006-06-28

Applicant: Daniel David Snook , John Herbert Dimmick , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin

Inventor： Daniel David Snook , John Herbert Dimmick , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin

IPC: F01D5/30

CPC classification number: F01D5/30 , F05D2230/10

Abstract: Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

Abstract translation: 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡燃气轮机叶片的机械性能。从材料去除区域去除材料会最大化平衡。

27.

发明授权
Conical tip shroud fillet for a turbine bucket 有权
Title translation: 涡轮桶锥形尖端护罩圆角
公开(公告)号：US07063509B2

公开(公告)日：2006-06-20

申请号：US10655623

申请日：2003-09-05

Applicant: Daniel David Snook , Peter Gaines Cleveland

Inventor： Daniel David Snook , Peter Gaines Cleveland

IPC: B63H1/16

CPC classification number: F01D5/225 , F01D5/141 , F05D2250/14 , F05D2250/16 , F05D2250/17 , F05D2250/232 , F05D2250/70 , F05D2250/74

Abstract: A turbine bucket airfoil has a conical fillet about the intersection of the airfoil tip and tip shroud having a nominal profile in accordance with coordinate values of X and Y, offset 1, offset 2 and Rho set forth in Table I. The shape parameters of offset 1, offset 2 and Rho define the configuration of the fillet at the specified X and Y locations about the fillet to provide a fillet configuration accommodating high localized stresses. The fillet shape may be parabolic, elliptical or hyperbolic as a function of the value of the shape parameter ratio of D1 D1 + D2 at each X, Y location where D1 is a distance between an intermediate point along a chord between edge points determined by offsets O1 and O2 and a shoulder point on the fillet surface and D2 is a distance between the shoulder point and an apex location at the intersection of the airfoil tip and tip shroud.

Abstract translation: 涡轮叶片翼型件根据X和Y，偏移1，偏移2和Rho的坐标值，具有围绕翼型尖端和尖端护罩的相交处的圆锥形圆角，其具有标称轮廓。偏移量的形状参数 1，偏移2和Rho定义圆角上指定的X和Y位置处的圆角的配置，以提供适应高局部应力的圆角配置。根据 $\frac{的形状参数比值的函数，圆角形状可以是抛物线形，椭圆形或双曲线}{D1D1+D228. 发明授权 Airfoil shape for a turbine bucket 有权 Title translation: 涡轮叶片的翼型公开(公告)号： US06857855B1 公开(公告)日： 2005-02-22 申请号： US10632853 申请日： 2003-08-04 Applicant: Daniel David Snook, Robert Romany By, Bruce Loren Smith, Gunnar Leif Siden, Carlos Alberto Collado, Peter Gaines Cleveland Inventor： Daniel David Snook, Robert Romany By, Bruce Loren Smith, Gunnar Leif Siden, Carlos Alberto Collado, Peter Gaines Cleveland IPC: F01D5/14 CPC classification number: F01D5/141, Y10S416/02 Abstract: Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0.03 span to 0.95 span convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the bucket airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of \pm0.150 inches in directions normal to the surface of the airfoil. Abstract translation: 第三级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值表示在表I中，其中X和Y值以英寸为单位，Z值是从0.03跨度到0.95跨度可变为Z的无量纲值通过将Z值乘以翼型件的高度（英寸），以英寸为单位。 X和Y值是通过平滑连续的弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成铲斗翼型形状。 X，Y和Z距离可以作为相同常数或数字的函数来缩放，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上在\pm0.150英寸的范围内。PDF内容加载中...« Previous page 123$(function(){
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} else {
// 添加 table-striped 和 Tabler风格类
content += '<table class="table table-striped table-hover table-borderless mb-0" style="width:500px">';
content += '<thead class="bg-light">';
content += ' <tr>';
content += ' <th style="width:120px">类型</th>';
content += ' <th style="width:100px">日期</th>';
content += ' <th>内容</th>';
content += ' </tr>';
content += '</thead>';
content += '<tbody>';

for (var i = 0; i < result.txs.length; i++) {
var tx = result.txs[i];
content += '<tr>';
content += ' <td><span class="badge bg-blue-lt">' + (tx.type || '--') + '</span></td>';
content += ' <td class="text-muted">' + (tx.executeDate || '--') + '</td>';
content += ' <td style="white-space:pre-line" class="small">' + (tx.htmlContent || tx.content || '') + '</td>';
content += '</tr>';
}

content += '</tbody></table>';
}

$content.html(content);
isLoaded = true;
$this.data('loaded', true);
},
error: function() {
$content.html('<div class="text-danger p-2">加载失败，请重试</div>');
$this.data('loaded', false); // 失败时重置状态
},
complete: function() {
$this.data('loading', false);
// 最终位置调整
$popover.css({
top: topPosition + 'px',
left: leftPosition + 'px'
});
}
});
});

// 鼠标离开处理（增强版）
var hideTimer;
$this.on('mouseleave', function() {
hideTimer = setTimeout(function() {
var $popover = $('#law-info-popover');
if (!$popover.is(':hover')) {
$popover.hide();

}
}, 300);
});

// Popover 悬停处理
$('#law-info-popover').hover(
function() {
clearTimeout(hideTimer);
},
function() {
$(this).hide();
}
);
});
});}$

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